EP2182289A2 - Method and apparatus for affecting a recirculation zone in a combustor cross flow - Google Patents
Method and apparatus for affecting a recirculation zone in a combustor cross flow Download PDFInfo
- Publication number
- EP2182289A2 EP2182289A2 EP09168267A EP09168267A EP2182289A2 EP 2182289 A2 EP2182289 A2 EP 2182289A2 EP 09168267 A EP09168267 A EP 09168267A EP 09168267 A EP09168267 A EP 09168267A EP 2182289 A2 EP2182289 A2 EP 2182289A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- flow
- cross flow
- outlet
- swozzle
- guide
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07001—Air swirling vanes incorporating fuel injectors
Definitions
- the subject matter disclosed herein relates generally to cross flow configurations. More particularly, the subject matter relates to fuel nozzles for gas turbine engines.
- a jet in cross flow occurs when a flow of fluid exits an orifice to interact with an intersecting flow of fluid that is flowing across the orifice. Jets in cross flow are central to a variety of applications such as gas turbine combustors, fuel injectors and pollution control in smoke stacks.
- a jet in cross flow typically creates a zone of recirculation downstream from where the cross flow is introduced. The recirculation zone typically has a reduced flow velocity that may cause a variety of detrimental effects depending on the configuration of the flow in cross flow application.
- a cross flow apparatus includes a surface, at least one outlet located at the surface, and at least one guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the at least one outlet downstream from the at least one outlet.
- a combustor swozzle includes a swozzle vane having a surface, a cross flow outlet located at the surface, and a guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the outlet downstream from the outlet.
- a method for combining a plurality of flows includes flowing a first flow of a first fluid across a surface, expelling a second flow of a second fluid from an opening in the surface into the first flow, guiding at least one of the first flow and the second flow and increasing a velocity of the second flow in a region downstream from where the second flow is expelled.
- the surface 130 has at least one cross flow outlet 140 thereon with two being illustrated in the Figure.
- a first flow 150 of compressed airflow approaches the leading edge 120 of the swozzle vane 110 and flows across the surface 130.
- a second flow 160 of combustor fuel is provided by a fuel chamber 170 and is thereafter expelled from the cross flow outlet 140 at an intersecting angle to the first flow 150.
- the swozzle vanes 110 may or may not be curved in profile up to ninety degrees downstream from the cross flow outlet 140 in order to mix and swirl the combination of the two flows 150, 160.
- a combustor (not shown) is thereafter receptive of the combination of the two flows 150, 160.
- On the surface 130 of at least one of the swozzle vanes 110 is at least one guiding portion 180, discussed herein.
- the guiding portion 180 is configured to direct the first flow 150 and thereby increase a velocity of the second flow 160 downstream from the cross flow outlet 140. This increased velocity reduces a zone of recirculation thereby decreasing flame holding therein.
- An embodiment disclosed herein is described by way of example with respect to a cross flow configuration on the surface 130 of the swozzle vane 110, but may be applied to any other cross flow configuration.
- the swozzle vane 110 is shown having the first flow 150 approaching the leading edge 120 that splits the first flow 150 into two flows.
- a portion of the first flow 150 flows across the surface 130 of the swozzle vane 110 shown in the Figures, while another portion of the first flow 150 flows across an antipodal surface (not shown) of the swozzle vane 110.
- the first flow 150 may be composed of compressed airflow as described hereinabove, but may alternately have flow and compositional properties of any type of intersecting flow that is configured to surround and intersect a cross flow. Regardless of the compositional properties of the intersecting flow 150, it is configured to flow across the cross flow outlets 140 on the surface 130 of swozzle vane 110.
- the cross flow outlets 140 are openings in the surface configured to expel the second flow 160 at an intersecting angle to the first flow 150.
- the second flow 160 is a jet of a combustible fuel such as gasoline, natural gas, propane, diesel, kerosene, E85, biodiesel, biogas, or by any other fuel used for combustion.
- the second flow 160 is any other flow of gaseous or liquid substance or combination thereof.
- the second flow 160 may have flow and compositional properties of any type of a cross flow introduced into a cross flow.
- Two of the cross flow outlets 140 are shown on the surface 130, each expelling the second flow 160.
- Each of the cross flow outlets 140 is shown herein to be generally circular.
- the cross flow outlet 140 may be ovular, polygonal or curved in shape, or a combination thereof. Further, it will be understood that one or more of the cross flow outlets 140 may also be included on the antipodal surface of the swozzle vane 110 in a similar configuration to the cross flow outlets 140 located on the surface 130.
- the swozzle vane 110 further includes at least one guiding portion 180, with two being illustrated about each one of the cross flow outlets 140.
- the guiding portion 180 is a guide that is configured to redirect the flow of at least one of the first flow 150 and the second flow 160. This redirection increases the velocity of the flow in a downstream region 190, the downstream region 190 located downstream from the cross flow outlet 140. This redirection further prevents both flame holding in the downstream region 190 and reduces a recirculation zone from forming in the downstream region 190.
- the guiding portion 180 increases the penetration height of the second flow 160 into the first flow 150 carrying the second flow 160 further the surface 130. This is useful in dispersing the fluid of the second flow 160 within the stream of the first flow 150.
- the guiding portion 180 further includes an upstream end 181 and a downstream end 182.
- the upstream end 181 is located farther than the downstream end 182 from a parallel flowline 200 that intersects the middle of the cross flow outlet 140 and is oriented parallel to the flow of the first flow 150.
- the guiding portion 180 is also curved around the cross flow outlet 140.
- the guiding portion 180 instead has a straight profile.
- the guiding portion 180 has two or more straight sections.
- the guiding portion 180 illustrated herein is a protruding vane
- the guiding portion 180 in alternate embodiments may be a negative impression or groove formed in the surface 130 around the cross flow outlet 140.
- the height of the guiding portion 180 normal to the surface 130 increases from upstream to downstream in one embodiment.
- the depth of the groove increases from upstream to downstream in one embodiment. It should be understood that the height and depth of the guiding portion is not limited to these embodiments but may remain constant or have any other configuration.
- a single of the at least one guiding portion 180 may be configured to increase the velocity of two or more of the second flows 160, with two being illustrated in the Figure.
- the single guiding portion 180 may be located between two or more of the cross flow outlets 140.
- the single guiding portion 180 may be a portion of sheet metal having two guiding walls 183.
- Each of the guiding walls 183 may have a profile and orientation similar to one of the protruding vanes in the previous embodiment described hereinabove.
- each of the two guiding walls 183 is configured to direct the first jet 150 to a position behind a separate one of the at least one cross jet outlets 140. It should be understood that these embodiments exemplify the guiding portion 180, but the guiding portion 180 is not limited to these embodiments.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Nozzles (AREA)
Abstract
Description
- The subject matter disclosed herein relates generally to cross flow configurations. More particularly, the subject matter relates to fuel nozzles for gas turbine engines.
- A jet in cross flow occurs when a flow of fluid exits an orifice to interact with an intersecting flow of fluid that is flowing across the orifice. Jets in cross flow are central to a variety of applications such as gas turbine combustors, fuel injectors and pollution control in smoke stacks. A jet in cross flow typically creates a zone of recirculation downstream from where the cross flow is introduced. The recirculation zone typically has a reduced flow velocity that may cause a variety of detrimental effects depending on the configuration of the flow in cross flow application.
- Thus, an apparatus that reduces, eliminates, or otherwise alters the recirculation zone downstream of a flow in cross flow would be well received in the art.
- According to one aspect of the invention, a cross flow apparatus includes a surface, at least one outlet located at the surface, and at least one guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the at least one outlet downstream from the at least one outlet.
- According to another aspect of the invention, a combustor swozzle includes a swozzle vane having a surface, a cross flow outlet located at the surface, and a guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the outlet downstream from the outlet.
- According to yet another aspect of the invention, a method for combining a plurality of flows includes flowing a first flow of a first fluid across a surface, expelling a second flow of a second fluid from an opening in the surface into the first flow, guiding at least one of the first flow and the second flow and increasing a velocity of the second flow in a region downstream from where the second flow is expelled.
- The subject matter which is regarded as the invention is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
-
Figure 1 depicts a perspective view of a combustor swozzle according to one embodiment of the present invention; -
Figure 2 depicts a perspective view of a swozzle vane in accordance with an embodiment of the present invention; -
Figure 3 depicts a cross sectional view of the swozzle vane ofFigure 2 taken at arrows 3-3; and -
Figure 4 depicts a perspective view of a swozzle vane in accordance with another embodiment of the present invention. - A detailed description of the hereinafter described embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures.
- Referring to
Figure 1 , there is shown acombustor swozzle 100 with a plurality ofswozzle vanes 110, each of theswozzle vanes 110 having a leadingedge 120 and asurface 130. Thesurface 130 has at least onecross flow outlet 140 thereon with two being illustrated in the Figure. During the combustion process in a gas turbine, afirst flow 150 of compressed airflow approaches the leadingedge 120 of theswozzle vane 110 and flows across thesurface 130. Asecond flow 160 of combustor fuel is provided by afuel chamber 170 and is thereafter expelled from thecross flow outlet 140 at an intersecting angle to thefirst flow 150. Theswozzle vanes 110 may or may not be curved in profile up to ninety degrees downstream from thecross flow outlet 140 in order to mix and swirl the combination of the two flows 150, 160. A combustor (not shown) is thereafter receptive of the combination of the two flows 150, 160. On thesurface 130 of at least one of theswozzle vanes 110 is at least one guidingportion 180, discussed herein. The guidingportion 180 is configured to direct thefirst flow 150 and thereby increase a velocity of thesecond flow 160 downstream from thecross flow outlet 140. This increased velocity reduces a zone of recirculation thereby decreasing flame holding therein. An embodiment disclosed herein is described by way of example with respect to a cross flow configuration on thesurface 130 of theswozzle vane 110, but may be applied to any other cross flow configuration. - Referring to
Figures 2 and3 , theswozzle vane 110 is shown having thefirst flow 150 approaching the leadingedge 120 that splits thefirst flow 150 into two flows. A portion of thefirst flow 150 flows across thesurface 130 of theswozzle vane 110 shown in the Figures, while another portion of thefirst flow 150 flows across an antipodal surface (not shown) of theswozzle vane 110. Thefirst flow 150 may be composed of compressed airflow as described hereinabove, but may alternately have flow and compositional properties of any type of intersecting flow that is configured to surround and intersect a cross flow. Regardless of the compositional properties of the intersectingflow 150, it is configured to flow across thecross flow outlets 140 on thesurface 130 ofswozzle vane 110. - In contrast, the
cross flow outlets 140 are openings in the surface configured to expel thesecond flow 160 at an intersecting angle to thefirst flow 150. In one embodiment, thesecond flow 160 is a jet of a combustible fuel such as gasoline, natural gas, propane, diesel, kerosene, E85, biodiesel, biogas, or by any other fuel used for combustion. In another embodiment, thesecond flow 160 is any other flow of gaseous or liquid substance or combination thereof. Thus, it will be understood that thesecond flow 160 may have flow and compositional properties of any type of a cross flow introduced into a cross flow. Two of thecross flow outlets 140 are shown on thesurface 130, each expelling thesecond flow 160. Each of thecross flow outlets 140 is shown herein to be generally circular. Alternately, thecross flow outlet 140 may be ovular, polygonal or curved in shape, or a combination thereof. Further, it will be understood that one or more of thecross flow outlets 140 may also be included on the antipodal surface of theswozzle vane 110 in a similar configuration to thecross flow outlets 140 located on thesurface 130. - The
swozzle vane 110 further includes at least one guidingportion 180, with two being illustrated about each one of thecross flow outlets 140. The guidingportion 180 is a guide that is configured to redirect the flow of at least one of thefirst flow 150 and thesecond flow 160. This redirection increases the velocity of the flow in adownstream region 190, thedownstream region 190 located downstream from thecross flow outlet 140. This redirection further prevents both flame holding in thedownstream region 190 and reduces a recirculation zone from forming in thedownstream region 190. Furthermore, the guidingportion 180 increases the penetration height of thesecond flow 160 into thefirst flow 150 carrying thesecond flow 160 further thesurface 130. This is useful in dispersing the fluid of thesecond flow 160 within the stream of thefirst flow 150. - In one embodiment, the guiding
portion 180 further includes anupstream end 181 and adownstream end 182. In this embodiment, theupstream end 181 is located farther than thedownstream end 182 from aparallel flowline 200 that intersects the middle of thecross flow outlet 140 and is oriented parallel to the flow of thefirst flow 150. The guidingportion 180 is also curved around thecross flow outlet 140. In another embodiment, rather than being curved, the guidingportion 180 instead has a straight profile. In yet another embodiment, the guidingportion 180 has two or more straight sections. - Although the guiding
portion 180 illustrated herein is a protruding vane, the guidingportion 180 in alternate embodiments may be a negative impression or groove formed in thesurface 130 around thecross flow outlet 140. In the case of a protruding guidingportion 180, the height of the guidingportion 180 normal to thesurface 130 increases from upstream to downstream in one embodiment. In the case of a negative impression groove, the depth of the groove increases from upstream to downstream in one embodiment. It should be understood that the height and depth of the guiding portion is not limited to these embodiments but may remain constant or have any other configuration. Furthermore, depending on the embodiment, there may be a plurality of the guidingportions 180 located about each of thecross flow outlets 140. In the illustrated embodiment, two of the guidingportions 180 are used for eachcross flow outlet 140, one on each side of thecross flow outlet 140. - Additionally, as depicted in
Figure 4 , a single of the at least one guidingportion 180 may be configured to increase the velocity of two or more of thesecond flows 160, with two being illustrated in the Figure. In this embodiment, the single guidingportion 180 may be located between two or more of thecross flow outlets 140. The single guidingportion 180 may be a portion of sheet metal having two guiding walls 183. Each of the guiding walls 183 may have a profile and orientation similar to one of the protruding vanes in the previous embodiment described hereinabove. However, each of the two guiding walls 183 is configured to direct thefirst jet 150 to a position behind a separate one of the at least onecross jet outlets 140. It should be understood that these embodiments exemplify the guidingportion 180, but the guidingportion 180 is not limited to these embodiments. - Elements of the embodiments have been introduced with either the articles "a" or "an." The articles are intended to mean that there are one or more of the elements. The terms "including" and "having" and their derivatives are intended to be inclusive such that there may be additional elements other than the elements listed. The conjunction "or" when used with a list of at least two terms is intended to mean any term or combination of terms. The terms "first" and "second" are used to distinguish elements and are not used to denote a particular order.
- While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
- For completeness, various aspects of the invention are now set out in the following numbered clauses:
- 1. A cross flow apparatus comprising:
- a surface;
- at least one outlet located at the surface; and
- at least one guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the at least one outlet downstream from the at least one outlet.
- 2. The cross flow apparatus of
clause 1, wherein the at least one guide is a protruding vane. - 3. The cross flow apparatus of
clause 1, wherein the at least one guide is a groove in the surface. - 4. The cross flow apparatus of
clause 1, wherein the at least one guide has an upstream end and a downstream end, the upstream end being located farther from a parallel flowline than the downstream end, the parallel flowline oriented parallel to a direction of the intersecting flow, the parallel flowline intersecting the middle of theat least one outlet. - 5. The cross flow apparatus of
clause 1, wherein the at least one guide is curved around the at least one outlet. - 6. The cross flow apparatus of
clause 1, wherein the at least one guide is two guides for each of the at least one outlet and the two guides are on opposing sides of the cross flow. - 7. The cross flow apparatus of
clause 1, wherein the at least one guide is configured to increase a penetration height of the cross flow further from the surface. - 8. The cross flow apparatus of
clause 1, wherein the cross flow includes combustible fuel. - 9. The cross flow apparatus of
clause 1, wherein the intersecting flow is compressed air. - 10. The cross flow apparatus of
clause 1, wherein the surface is located on a swozzle vane. - 11. The cross flow apparatus of
clause 1, further comprising a combustor receptive to the combination of the cross flow and the intersecting flow. - 12. The cross flow apparatus of
clause 1, wherein at least one of the at least one guide is configured to increase the velocity of a plurality of cross flows. - 13. A combustor swozzle comprising:
- a swozzle vane having a surface;
- an outlet located at the surface; and
- a guide at the surface configured to direct an intersecting flow flowing across the surface and increase a velocity of a cross flow being expelled from the outlet downstream from the outlet.
- 14. The combustor swozzle of clause 13, wherein the swozzle vane has two antipodal surfaces, each of the surfaces having at least one outlet.
- 15. The combustor swozzle of clause 13, wherein the swozzle vane has a curved profile.
- 16. The combustor swozzle of clause 13, further comprising a plurality of swozzle vanes.
- 17. A method for combining a plurality of flows comprising:
- flowing a first flow of a first fluid across a surface;
- expelling a second flow of a second fluid from an opening in the surface into the first flow;
- guiding at least one of the first flow and the second flow; and
- increasing a velocity of the second flow in a region downstream from where the second flow is expelled.
- 18. The method for combining a plurality of flows of clause 17, further comprising reducing flame holding in the region downstream from the opening.
- 19. The method for combining a plurality of flows of clause 17, further comprising reducing the formation of a recirculation zone in the region downstream from the opening.
- 20. The method for combining a plurality of flows of clause 17, further comprising increasing a penetration height of the first flow further from the opening.
Claims (15)
- A cross flow apparatus (100) comprising:a surface (130);at least one outlet (140) located at the surface (130); andat least one guide (180) at the surface (130) configured to direct an intersecting flow (150) flowing across the surface (130) and increase a velocity of a cross flow (160) being expelled from the at least one outlet (140) downstream from the at least one outlet (140).
- The cross flow apparatus (100) of claim 1, wherein the at least one guide (180) is a protruding vane.
- The cross flow apparatus (100) of claim 1 or 2, wherein the at least one guide (180) is a groove in the surface (130).
- The cross flow apparatus (100) of any of the preceding claims, wherein the at least one guide (180) has an upstream end (181) and a downstream end (182), the upstream end (181) being located farther from a parallel flowline (200) than the downstream end (182), the parallel flowline (200) oriented parallel to a direction of the intersecting flow (150), the parallel flowline (200) intersecting the middle of the at least one outlet (140).
- The cross flow apparatus (100) of any of the preceding claims, wherein the at least one guide (180) is curved around the at least one outlet (140).
- The cross flow apparatus of any of the preceding claims, wherein the at least one guide is two guides for each of the at least one outlet and the two guides are on opposing sides of the cross flow.
- The cross flow apparatus of any of the preceding claims, wherein the at least one guide is configured to increase a penetration height of the cross flow further from the surface.
- The cross flow apparatus of any of the preceding claims, wherein the cross flow includes combustible fuel.
- A combustor swozzle (100) comprising:a swozzle vane (110) having a surface (130);an outlet (140) located at the surface (130); anda guide (180) at the surface (130) configured to direct an intersecting flow (150) flowing across the surface (130) and increase a velocity of a cross flow (160) being expelled from the outlet (140) downstream from the outlet (140).
- The combustor swozzle (100) of claim 9, wherein the swozzle vane (110) has two antipodal surfaces (130), each of the surfaces (130) having at least one outlet (140).
- The combustor swozzle (100) of claim 9 or 10, wherein the swozzle vane (110) has a curved profile.
- A method for combining a plurality of flows comprising:flowing a first flow (150) of a first fluid across a surface (130);expelling a second flow (160) of a second fluid from an opening in the surface (130) into the first flow (150);guiding at least one of the first flow (150) and the second flow (160); andincreasing a velocity of the second flow (160) in a region downstream (190) from where the second flow (160) is expelled.
- The method for combining a plurality of flows of claim 12, further comprising reducing the formation of a recirculation zone in the region downstream (190) from the opening.
- The method for combining a plurality of flows of claim 12 or 13, further comprising reducing flame holding in the region downstream from the opening.
- The method for combining a plurality of flows of any of claims 12 to 14, further comprising increasing a penetration height of the first flow further from the opening.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/262,358 US8220270B2 (en) | 2008-10-31 | 2008-10-31 | Method and apparatus for affecting a recirculation zone in a cross flow |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2182289A2 true EP2182289A2 (en) | 2010-05-05 |
EP2182289A3 EP2182289A3 (en) | 2013-05-01 |
Family
ID=41629866
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09168267.4A Withdrawn EP2182289A3 (en) | 2008-10-31 | 2009-08-20 | Method and apparatus for affecting a recirculation zone in a combustor cross flow |
Country Status (4)
Country | Link |
---|---|
US (1) | US8220270B2 (en) |
EP (1) | EP2182289A3 (en) |
JP (1) | JP2010107186A (en) |
CN (1) | CN101726003A (en) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8851402B2 (en) * | 2009-02-12 | 2014-10-07 | General Electric Company | Fuel injection for gas turbine combustors |
US20100287938A1 (en) * | 2009-05-14 | 2010-11-18 | General Electric Company | Cross flow vane |
JP5948489B2 (en) | 2013-03-13 | 2016-07-06 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
US9516890B2 (en) | 2013-03-14 | 2016-12-13 | Denso International America, Inc. | Rib maze that prevents flow along a wall |
US9453461B2 (en) | 2014-12-23 | 2016-09-27 | General Electric Company | Fuel nozzle structure |
US10739006B2 (en) | 2017-03-15 | 2020-08-11 | General Electric Company | Fuel nozzle for a gas turbine engine |
US10775048B2 (en) | 2017-03-15 | 2020-09-15 | General Electric Company | Fuel nozzle for a gas turbine engine |
KR101967052B1 (en) * | 2017-07-06 | 2019-04-08 | 두산중공업 주식회사 | Nozzle for combustor and gas turbine having the same |
KR102024542B1 (en) * | 2017-07-14 | 2019-09-24 | 두산중공업 주식회사 | Nozzle for combustor and gas turbine having the same |
KR102162053B1 (en) | 2019-03-25 | 2020-10-06 | 두산중공업 주식회사 | Nozzle assembly and gas turbine including the same |
KR102096580B1 (en) | 2019-04-01 | 2020-04-03 | 두산중공업 주식회사 | Combustion nozzle enhancing spatial uniformity of pre-mixture and gas turbine having the same |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1367329A1 (en) * | 2001-03-09 | 2003-12-03 | Osaka Gas Co., Ltd. | Burner and gas turbine engine |
US20040050061A1 (en) * | 2002-09-13 | 2004-03-18 | Schmotolocha Stephen N. | Compact swirl augmented afterburners for gas turbine engines |
GB2435508A (en) * | 2006-02-22 | 2007-08-29 | Siemens Ag | A swirler for use in a burner of a gas turbine engine |
US20080083229A1 (en) * | 2006-10-06 | 2008-04-10 | General Electric Company | Combustor nozzle for a fuel-flexible combustion system |
EP1916481A2 (en) * | 2006-09-29 | 2008-04-30 | General Electric Company | Premixing device, gas turbines comprising the premixing device, and methods of use |
EP1985923A2 (en) * | 2007-04-27 | 2008-10-29 | General Electric Company | Methods and systems to facilitate reducing flashback/flame holding in combustion systems |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5251447A (en) * | 1992-10-01 | 1993-10-12 | General Electric Company | Air fuel mixer for gas turbine combustor |
DE19520291A1 (en) * | 1995-06-02 | 1996-12-05 | Abb Management Ag | Combustion chamber |
GB2333832A (en) * | 1998-01-31 | 1999-08-04 | Europ Gas Turbines Ltd | Multi-fuel gas turbine engine combustor |
GB9818160D0 (en) * | 1998-08-21 | 1998-10-14 | Rolls Royce Plc | A combustion chamber |
US6405536B1 (en) | 2000-03-27 | 2002-06-18 | Wu-Chi Ho | Gas turbine combustor burning LBTU fuel gas |
JP2002213746A (en) * | 2001-01-19 | 2002-07-31 | Mitsubishi Heavy Ind Ltd | Burner, premix fuel nozzle of combustor, and an combustor |
US6691515B2 (en) * | 2002-03-12 | 2004-02-17 | Rolls-Royce Corporation | Dry low combustion system with means for eliminating combustion noise |
US7350357B2 (en) * | 2004-05-11 | 2008-04-01 | United Technologies Corporation | Nozzle |
US6993916B2 (en) * | 2004-06-08 | 2006-02-07 | General Electric Company | Burner tube and method for mixing air and gas in a gas turbine engine |
US7415827B2 (en) * | 2005-05-18 | 2008-08-26 | United Technologies Corporation | Arrangement for controlling fluid jets injected into a fluid stream |
EP2041494B8 (en) * | 2005-12-14 | 2015-05-27 | Industrial Turbine Company (UK) Limited | Gas turbine engine premix injectors |
GB2437977A (en) * | 2006-05-12 | 2007-11-14 | Siemens Ag | A swirler for use in a burner of a gas turbine engine |
EP1867925A1 (en) * | 2006-06-12 | 2007-12-19 | Siemens Aktiengesellschaft | Burner |
EP1890083A1 (en) * | 2006-08-16 | 2008-02-20 | Siemens Aktiengesellschaft | Fuel injector for a gas turbine engine |
-
2008
- 2008-10-31 US US12/262,358 patent/US8220270B2/en active Active
-
2009
- 2009-08-20 EP EP09168267.4A patent/EP2182289A3/en not_active Withdrawn
- 2009-08-27 JP JP2009196165A patent/JP2010107186A/en not_active Ceased
- 2009-08-31 CN CN200910168959A patent/CN101726003A/en active Pending
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1367329A1 (en) * | 2001-03-09 | 2003-12-03 | Osaka Gas Co., Ltd. | Burner and gas turbine engine |
US20040050061A1 (en) * | 2002-09-13 | 2004-03-18 | Schmotolocha Stephen N. | Compact swirl augmented afterburners for gas turbine engines |
GB2435508A (en) * | 2006-02-22 | 2007-08-29 | Siemens Ag | A swirler for use in a burner of a gas turbine engine |
EP1916481A2 (en) * | 2006-09-29 | 2008-04-30 | General Electric Company | Premixing device, gas turbines comprising the premixing device, and methods of use |
US20080083229A1 (en) * | 2006-10-06 | 2008-04-10 | General Electric Company | Combustor nozzle for a fuel-flexible combustion system |
EP1985923A2 (en) * | 2007-04-27 | 2008-10-29 | General Electric Company | Methods and systems to facilitate reducing flashback/flame holding in combustion systems |
Also Published As
Publication number | Publication date |
---|---|
JP2010107186A (en) | 2010-05-13 |
CN101726003A (en) | 2010-06-09 |
US8220270B2 (en) | 2012-07-17 |
EP2182289A3 (en) | 2013-05-01 |
US20100107641A1 (en) | 2010-05-06 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2182289A2 (en) | Method and apparatus for affecting a recirculation zone in a combustor cross flow | |
EP3201446B1 (en) | Ducted fuel injection | |
EP2218966B1 (en) | Fuel injection for gas turbine combustors | |
EP1400753B1 (en) | Flashback resistant pre-mix burner for a gas turbine combustor | |
US8579214B2 (en) | Swirler vane | |
EP2728261B1 (en) | Burner with axial swirler and method for operating said burner | |
EP2660520A2 (en) | Fuel/air premixing system for turbine engine | |
US10352567B2 (en) | Fuel-air premixer for a gas turbine | |
CA2630721A1 (en) | Gas turbine engine premix injectors | |
US8967852B2 (en) | Mixers for immiscible fluids | |
EP1985924A1 (en) | Swirler | |
EP1921376A1 (en) | Fuel injection system | |
US8291705B2 (en) | Ultra low injection angle fuel holes in a combustor fuel nozzle | |
US20170328568A1 (en) | Fuel lance with means for interacting with a flow of air and improve breakage of an ejected liquid jet of fuel | |
EP1995521A1 (en) | Swirler vane | |
CN101886554A (en) | Cross flow vane | |
KR20160063272A (en) | Burner of a gas turbine | |
EP2584267B1 (en) | Injector having multiple fuel pegs | |
JP2017089574A (en) | Fuel injection valve of internal combustion engine, and internal combustion engine | |
JP4877735B2 (en) | Boiler equipment | |
JP2000346360A (en) | Gas turbine premixing duct |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK SM TR |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: F23R 3/14 20060101ALI20130326BHEP Ipc: F02K 1/46 20060101ALI20130326BHEP Ipc: F23R 3/20 20060101ALI20130326BHEP Ipc: F23R 3/28 20060101AFI20130326BHEP |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20131105 |